Device and method for supplying fuel to an aircraft, or an aerostat equipped with it

Abstract

The invention relates to a hydrogen supply device comprising a low-pressure hydrogen tank (3), a water tank (5), a fuel cell (2), and an electrolyzer (6), characterized in that the device includes a switch (10) for switching an electrical circuit (200) of the aircraft either to the power output (24) of the fuel cell (2) in a first switching position, or to the power input (69) of the electrolyzer (6) in a second switching position. Figure 1

Description

Title of the invention: Device and method for supplying fuel to an aircraft, aerostat equipped therewith

[0001] The invention relates to a power supply device for an aircraft which may be of the aerostat type equipped with it.

[0002] The field of the invention relates in particular to dirigible aerostats.

[0003] Aircraft, which may be of the aerostat type, require a power supply device which must be on board for their propulsion.

[0004] One of the problems with these power supply devices is increasing their autonomy.

[0005] An objective of the invention is to obtain a power supply device for an aircraft and an aerostat equipped with it, which solve the problem mentioned above.

[0006] To this end, a first object of the invention is a hydrogen supply device for an aircraft, the device comprising at least one low-pressure hydrogen tank, at least one water tank, at least one fuel cell, comprising at least one hydrogen inlet duct, which is connected to the hydrogen tank, at least one oxygen inlet duct and at least one water discharge duct, which is emitted by the combustion of hydrogen by the fuel cell, to generate electricity on at least one electricity production output of the fuel cell, the water discharge duct being connected to the water tank, at least one electrolyzer, comprising at least one water inlet pipe, which is connected to the water tank, at least one hydrogen discharge pipe produced by electrolysis of water in the electrolyzer, which is connected to the first hydrogen tank, at least one oxygen discharge pipe produced by electrolysis of water in the electrolyzer and at least one power supply input, characterized in that the device further comprises at least one switch configured to switch an electrical circuit of the aircraft either to the power output of the fuel cell in a first switching position, or to the power input of the electrolyzer in a second switching position, The switch can be controlled to be in either the first or second switching position. Thanks to the invention, the power supply device can adopt the first switching position at night to supply electricity via the fuel cell to the aircraft's electrical circuit, which operates from the low-pressure hydrogen tank. The device The power supply can adopt the second switching position during the day, so that the electrolyzer is powered by the aircraft's electrical system and produces hydrogen, which is sent to the low-pressure hydrogen tank. This increases the aircraft's range.

[0007] According to one embodiment of the invention, the switch comprises a first electrical terminal connected to the electricity production output of the fuel cell, a second electrical terminal connected to the electricity supply input of the electrolyzer, and a third electrical terminal connected to at least one electrical circuit of the aircraft, in the first switching position the switch connecting the third electrical terminal to the first electrical terminal and the third electrical terminal not being connected to the second electrical terminal, to operate the fuel cell on the aircraft's electrical circuit without operating the electrolyzer, and in the second switching position the switch connecting the third electrical terminal to the second electrical terminal and the third electrical terminal not being connected to the first electrical terminal, to operate the electrolyzer on the aircraft's electrical circuit without operating the fuel cell.

[0008] According to one embodiment of the invention, the device includes at least one electrical converter connected between the third electrical terminal of the switch and the electrical circuit of the aircraft.

[0009] According to one embodiment of the invention, the third electrical terminal of the switch is connected to at least one electrically consuming device of the aircraft's electrical circuit in the first switching position.

[0010] According to one embodiment of the invention, the third electrical terminal of the switch is connected to at least one electrical supply device for the aircraft's electrical circuit in the second switching position.

[0011] According to one embodiment of the invention, the electrical supply device for the aircraft's electrical circuit includes at least one photovoltaic panel.

[0012] According to one embodiment of the invention, at least one water condenser is interposed on the water ejection conduit to send liquid water through the water ejection conduit to the liquid water reservoir.

[0013] According to one embodiment of the invention, the supply device comprises a first circulation circuit of a first heat transfer fluid for cooling the water condenser, the first circulation circuit of the first heat transfer fluid passing through or against the water condenser and comprising at least one first heat exchanger capable of removing heat from the water condenser via at least one first passage for the first heat transfer fluid. carrier of the first circuit.

[0014] According to one embodiment of the invention, the first heat exchanger is of the grid and / or fin type and includes at least one air fan, capable of supplying heat via air to the first heat exchanger.

[0015] According to one embodiment of the invention, the power supply device includes a second circulation circuit of a second heat transfer fluid for cooling the fuel cell and the electrolyzer, the second circulation circuit of the second heat transfer fluid passing through or against the fuel cell and through or against the electrolyzer and comprising at least one second heat exchanger capable of extracting heat from the fuel cell and the electrolyzer via at least one second passage channel for the second heat transfer fluid of the second circuit.

[0016] According to one embodiment of the invention, the second heat exchanger is of the grid and / or fin type and includes at least one air fan, capable of extracting heat from the second heat exchanger via the air.

[0017] According to one embodiment of the invention, the first heat exchanger is separated from the second heat exchanger.

[0018] According to another embodiment of the invention, the first heat exchanger is connected to the second heat exchanger.

[0019] According to one embodiment of the invention, at least one pressure regulator is interposed on the hydrogen ejection conduit for sending the hydrogen produced by the electrolyzer to the first hydrogen reservoir with a reduction of the hydrogen pressure from the electrolyzer to the low-pressure hydrogen reservoir.

[0020] According to one embodiment of the invention, the low-pressure hydrogen tank contains hydrogen in a gaseous state.

[0021] According to one embodiment of the invention, the low-pressure hydrogen tank contains hydrogen in a gaseous state at a pressure 100 to 500 mbar higher than the ambient pressure.

[0022] According to one embodiment of the invention, the oxygen supply duct is connected to an ambient air inlet.

[0023] According to one embodiment of the invention, the feeding device further comprises at least one oxygen reservoir, which is connected to the oxygen ejection conduit to receive oxygen produced by the electrolyzer.

[0024] According to one embodiment of the invention, the feeding device further comprises an oxygen reservoir, which is connected to the oxygen ejection duct to receive oxygen produced by the electrolyzer, The oxygen supply line is connected to an ambient air intake and to another oxygen supply line from the oxygen tank to allow the sending oxygen from both the ambient air intake and the oxygen reservoir to the oxygen supply duct.

[0025] According to one embodiment of the invention, the oxygen supply duct is connected to the ambient air inlet and to the other oxygen supply duct from the oxygen reservoir at least via an air regulator.

[0026] According to one embodiment of the invention, the feeding device comprises at least one water pump on the water inlet conduit for sending water from the liquid water reservoir to the electrolyzer, a first motor having a rotating shaft for driving the water pump, and at least one blade, which is disposed in the hydrogen ejection conduit and which is driven in rotation about an axis of rotation by the hydrogen flow going from the electrolyzer to the hydrogen reservoir in the hydrogen ejection conduit, the drive shaft of the first water pump drive motor being coupled to the axis of rotation of the blade to recover the energy of the blade.

[0027] According to one embodiment of the invention, the electrolyzer, the water inlet duct and the liquid water reservoir form part of a first unit, the low pressure hydrogen reservoir, the fuel cell, the hydrogen inlet duct, the oxygen inlet duct and the water condenser form part of a second unit, which is separable from the first unit.

[0028] According to one embodiment of the invention, an initial mass of gaseous hydrogen is contained in the hydrogen tank.

[0029] According to one embodiment of the invention, the electrolyzer can be formed by a reversible module that can operate either as an electrolyzer or as a fuel cell.

[0030] A second object of the invention is an aircraft or dirigible aerostat, comprising at least one power supply device as described above.

[0031] A third object of the invention is a method of supplying hydrogen to an aircraft using the supply device as described above, characterized in that the switch is controlled either in the first switching position or in the second switching position.

[0032] The invention will be better understood upon reading the following description, given solely by way of non-limiting example with reference to the figures below of the attached drawings.

[0033] [Fig. 1] represents a modular block diagram of a first power supply device hydrogen according to an embodiment of the invention.

[0034] [Fig.2] represents a modular block diagram of a second power supply device in hydrogen according to an embodiment of the invention.

[0035] [Fig.3] represents a modular block diagram of a third power supply device in hydrogen according to an embodiment of the invention.

[0036] [Fig.4] represents a modular block diagram of a fourth power supply device in hydrogen according to an embodiment of the invention.

[0037] [Fig.5] represents a modular block diagram of a fifth power supply device in hydrogen according to an embodiment of the invention.

[0038] [Fig.6] represents a cross-sectional diagram of a hydrogen tank following a mode of the realization of the invention.

[0039] In what follows, hydrogen is considered to be dihydrogen.

[0040] In figures 1 to 6, the hydrogen supply device 1 according to the invention comprises one (or more) low-pressure hydrogen reservoir 3 and one (or more) liquid water reservoir 5.

[0041] The hydrogen supply device 1 according to the invention can be provided on board an aircraft, and for example on board a dirigible, or other. The hydrogen supply device 1 according to the invention has the function of supplying energy to the aircraft or dirigible, for example for its propulsion at least from back to front by means of one (or more) propulsion engine on board the aircraft or dirigible.

[0042] The hydrogen supply device 1 includes one (or more) fuel cell 2 consuming hydrogen from the low-pressure hydrogen tank 3 to generate electricity and one (or more) electrolyzer 6 consuming water from the liquid water tank 5 to return hydrogen to the hydrogen tank 3.

[0043] The fuel cell 2 is connected to one (or more) hydrogen inlet line 21 connected to the hydrogen tank 3 to supply hydrogen from the tank 3 to the fuel cell 2. The fuel cell 2 is connected to one (or more) oxygen inlet line 22 to supply oxygen to the fuel cell 2. The fuel cell 2 combusts the hydrogen supplied in line 21 with the oxygen supplied in line 22 to generate electricity at one (or more) power output 24 of the fuel cell 2 and to generate water at the water discharge line 23. The fuel cell 2 is connected to one (or more) water discharge line 23, which discharges the liquid water produced by the combustion of hydrogen and oxygen from the fuel cell 2 to the liquid water tank 5.

[0044] The electrolyzer 6 is connected to one (or more) water inlet pipe 61 connected to the liquid water reservoir 5 to send liquid water from the reservoir 5 to the electrolyzer 6. The electrolyzer 6 performs the electrolysis of water to generate hydrogen and oxygen. The electrolyzer 6 is connected to one (or more) hydrogen discharge pipe 62 for the ejection of the hydrogen produced by the electrolysis of water in the electrolyzer 6. The hydrogen discharge pipe 62 is connected to the hydrogen reservoir 3, to send the hydrogen produced by the electrolysis of water in the electrolyzer 6 to the hydrogen reservoir 3. The electrolyzer 6 is connected to one (or more) conduit 63 for the ejection of oxygen produced by the electrolysis of water in the electrolyzer 6. The electrolyzer 6 has one (or more) input 69 for supplying electricity.

[0045] In Figures 1 to 5, the device 1 includes one (or more) switch 10 for switching an electrical circuit 200 of the aircraft either to the power output 24 of the fuel cell 2 in a first switching position (for example, at night), or to the power input 69 of the electrolyzer 6 in a second switching position (for example, during the day). In Figures 1 to 5, the switch 10 is shown in the second switching position. The switch 10 has a first electrical terminal 101 connected to the power output 24 of the fuel cell 2, a second electrical terminal 102 connected to the power input 69 of the electrolyzer 6, and a third electrical terminal 103 connected to at least one electrical circuit 200 of the aircraft.

[0046] In the first switching position, the switch 10 connects (via a conductor 104 or a second electronic circuit 104 or otherwise) the third electrical terminal 103 to the first electrical terminal 101, and the third electrical terminal 103 is not connected to the second electrical terminal 102. Thus, in this first switching position, the fuel cell 2 is operated on the aircraft's electrical circuit 200 without operating the electrolyzer 6, so that the fuel cell 2 sends electricity to the aircraft's electrical circuit 200, for example, to the propulsion engine(s) of the aircraft or airship and / or to auxiliary electrical systems of the aircraft or airship. The power supply device 1 thus provides electrical power from low-pressure or unpressurized hydrogen.This allows the fuel cell on board the aircraft (e.g., airship or other) to be supplied with hydrogen in a simple, efficient way, while reducing the onboard mass.

[0047] In the second switching position, the switch 10 connects (via a conductor 104 or second electronic circuit or other) the third electrical terminal 103 to the second electrical terminal 102 and the third electrical terminal 103 is not connected to the first electrical terminal 101. Thus, in this second switching position, the electrolyzer 6 is operated on the aircraft's electrical circuit 200 without operating the fuel cell 2, so that the aircraft's electrical circuit 200 sends electricity to the electrolyzer 6. This allows hydrogen to be generated autonomously.

[0048] One (or more) control inputs 105 are provided on the switch 10 to place the switch 10 either in the first switching position or in the second switching position. The switch 10 can thus be actuated by a user either in the first switching position or in the second switching position.

[0049] In a method of supplying hydrogen to the aircraft using the supply device 1, the user controls the switch 10 either in the first switching position or in the second switching position.

[0050] According to one embodiment shown in Figures 1 to 5, the device comprises at least one electrical converter 9 connected between the switch 10 and the aircraft's electrical circuit 200. The electrical converter 9 is connected between the third electrical terminal 103 of the switch 10 and an electrical interface 240 of the aircraft's electrical circuit 200. The electrical converter 9 may be bidirectional and is, for example, a DC-DC converter. The electrical converter 9 allows either the electrical output 24 of the battery 2 to be regulated in the second switching position, or the electrical input 69 of the electrolyzer 6 in the first switching position.

[0051] According to one embodiment, shown in Figures 1 to 5, the aircraft's electrical circuit 200 includes one (or more) electrically consuming device 201. The third electrical terminal 103 of the switch 10 is connected to the electrically consuming device 201 in the first switching position.

[0052] According to one embodiment, shown in Figures 1 to 5, the aircraft's electrical circuit 200 comprises one (or more) power supply device 202. The third electrical terminal 103 of the switch 10 is connected to the power supply device 202 in the second switching position.

[0053] As shown in figures 1 to 5, the aircraft's electrical circuit 200 may include both the electrical consumption device 201 and the electrical supply device 202.

[0054] According to one embodiment shown in Figures 1 to 5, the aircraft's electrical circuit 200 power supply device 202 comprises one (or more) photovoltaic panel 203. This allows the electrolyzer 6 to be powered in its second switching position during the day. Of course, the aircraft's electrical circuit 200 power supply device 202 may, in addition to or instead of the photovoltaic panel 203, include other power supply devices 202, such as one (or more) electric battery 202 or others.

[0055] According to one embodiment, shown in Figures 1 to 5, the supply device 1 includes one (or more) water condenser 4 interposed on the water discharge conduit 23, to send liquid water through the water discharge conduit 23 to the liquid water reservoir 5. The water condenser 4 may or may not include a water extractor and / or a water separator. The condenser 4 cools the water + air mixture to condense the water and thus increase the size of the water drops and facilitate the recovery of the water (by centrifugation for example) in the water ejection conduit 23.

[0056] The supply device 1 thus makes it possible to recover energy from the hydrogen reservoir 3 under different atmospheric conditions, the water condenser 4 making it possible to send the water in liquid form through the water ejection conduit 23 into the liquid water reservoir 5 at more or less low temperatures, including below 0° C, thus making a hydrogen recovery loop via the liquid water circulation circuit formed by the conduits 61 and 23. Indeed, frozen water could not be returned through the conduit 23 to the reservoir 5. Thus, the water condenser 4 also prevents the water from freezing.

[0057] Embodiments of the water condenser 4 are described below, with reference to figures 1 to 5.

[0058] According to one embodiment, shown in Figures 1 to 5, the supply device 1 comprises a first circulation circuit 40 of a first heat transfer fluid for cooling the water condenser 4. The first circulation circuit 40 of the first heat transfer fluid for cooling the water condenser 4 passes through or against the water condenser 4. The first circulation circuit 40 of the first heat transfer fluid for cooling the water condenser 4 comprises one (or more) first heat exchanger 41 capable of cooling the water condenser 4 via one (or more) first pipe 42, 43, through which the first heat transfer fluid of the first circuit 40 passes. The first heat exchanger 41 cools the first heat transfer fluid and sends the cooled first heat transfer fluid through the pipe 42 to the water condenser 4.In or near the water condenser 4, the first cooled heat transfer fluid absorbs heat from the water condenser 4 to cool the water supplied to the pipe 23. The first heat transfer fluid, having been heated in the water condenser 4, is returned in the pipe 43 to the first heat exchanger 41.

[0059] In Figures 1 to 5, the first water-cooling heat transfer fluid of the condenser 4 can be, for example, glycol water or oil or other.

[0060] According to one embodiment, shown in Figures 1 to 5, the first heat exchanger 41 is of the grid and / or fin type. The first heat exchanger 41 includes one (or more) air fan 45. The air fan 45 passes outside air against a surface 46 of the first heat exchanger 41, supplying it with heat.

[0061] According to one embodiment, shown in Figures 1 to 5, the power supply device 1 includes a second circulation circuit 70 for a second heat transfer fluid for cooling the fuel cell 2 and the electrolyzer 6. The second circulation circuit 70 passes the second heat transfer fluid through or against the fuel cell 2 and through or against the electrolyzer 6. The second circulation circuit 70 The system for circulating a second heat transfer fluid for cooling the fuel cell 2 and the electrolyzer 6 includes one (or more) second heat exchanger 71 capable of extracting heat from the fuel cell 2 and the electrolyzer 6 via one (or more) second pipe 72, 73, 74, through which the second heat transfer fluid of the second circuit 70 passes. In or near the electrolyzer 6, the second heat transfer fluid absorbs heat from the electrolyzer 6. The second heat transfer fluid, having been heated in the electrolyzer 6, is sent through pipe 74 to the fuel cell 2. In or near the fuel cell 2, the second heat transfer fluid absorbs heat from the fuel cell 2. The second heat transfer fluid, having been heated in the fuel cell 2, is sent in the pipe 72 to the second heat exchanger 71.The second heat transfer fluid, having been cooled by the second heat exchanger 71, is returned in the pipe 73 to the electrolyzer 6.

[0062] In Figures 1 to 5, the second heat transfer fluid for cooling the electrolyzer 6 and the fuel cell 2 can be, for example, glycol water or oil or other.

[0063] According to one embodiment, shown in Figures 1 to 5, the second heat exchanger 71 is of the grid and / or fin type. The second heat exchanger 71 includes one (or more) second air fan 45. The second air fan blows outside air against a surface 76 of the second heat exchanger 71, cooling it.

[0064] According to one embodiment, not shown, the first heat exchanger 41 is separated from the second heat exchanger 71.

[0065] According to one embodiment, in figures 1 to 5, the first heat exchanger 41 is connected to the second heat exchanger 71.

[0066] According to one embodiment, in figures 1 to 5, the water condenser 4 may include an air exhaust duct 47 to the outside, to exhaust to the outside the air sent by the air fan 45.

[0067] According to one embodiment, shown in Figures 1, 2 and 5, one (or more) pressure regulator 620 is interposed on the hydrogen ejection conduit 62 to send the hydrogen produced by the electrolyzer 6 to the first hydrogen reservoir 3. The pressure regulator 620 reduces the hydrogen pressure from the electrolyzer 6 to the low-pressure hydrogen reservoir 3.

[0068] According to one embodiment, in figures 1 to 5, the low-pressure hydrogen reservoir 3 contains hydrogen in the gaseous state.

[0069] According to one embodiment, shown in Figures 1 to 5, the low-pressure hydrogen reservoir 3 is formed by one (or more) gas envelope 30 of a dirigible aerostat, This gas contains hydrogen. The gas envelope 30 is slightly or unpressurized. The airship may include one (or more) hydrogen envelopes 30 forming the low-pressure hydrogen reservoir 3. In the embodiment of [Fig. 6], the airship may include the hydrogen envelope 30 located within another envelope 31, itself filled with helium, in the space 310 situated between the envelope 30 and the other envelope 31. Of course, the envelope 30 may be different from this embodiment of [Fig. 6].

[0070] According to one embodiment, in figures 1 to 5, the low-pressure hydrogen reservoir 3 has hydrogen in the gaseous state at a pressure equal to or slightly above the ambient air pressure of the surrounding atmosphere, and in particular on the order of a pressure 100 to 500 mbar above the ambient pressure.

[0071] According to one embodiment, in figures 1 to 5, the supply device 1 includes one (or more) compressor 32 on the hydrogen inlet conduit 21, to compress the hydrogen from the hydrogen tank 3 towards the fuel cell 2.

[0072] According to one embodiment, in figures 1 to 5, the supply device 1 includes one (or more) air or oxygen compressor 28 on the oxygen or air supply conduit 22, to compress the oxygen or air towards the fuel cell 2.

[0073] According to one embodiment, in figures 1 to 5, the oxygen supply conduit 22 is connected to an ambient air inlet 25.

[0074] According to one embodiment, in figures 2 and 4, the supply device 1 includes one (or more) oxygen reservoir 8, which is connected to the oxygen ejection conduit 63 to store the oxygen produced by the electrolyzer 6. The oxygen is stored in gaseous form in the reservoir 8.

[0075] According to one embodiment, in figures 2 and 4, the oxygen reservoir 8 is connected to another conduit 26 sending oxygen from the oxygen reservoir 8 to the oxygen supply conduit 22.

[0076] According to one embodiment, shown in Figures 2 and 4, the oxygen supply line 22 is connected to an ambient air inlet 25 and to another line 26 to allow oxygen to be supplied both from the ambient air inlet 25 and from the oxygen reservoir 8 to the oxygen supply line 22. This allows the fuel cell 2 to be started at altitude. Indeed, one problem is delivering high power from an air compressor 28 to supply oxygen to the fuel cell 2 at altitude. This allows pure oxygen to be supplied to the fuel cell 2 at altitude from the oxygen reservoir 8, for a backup function, for example.

[0077] According to one embodiment, in Figures 2 and 4, the oxygen supply duct 22 is connected to the ambient air inlet 25 and to the other duct 26 at least via of an air regulator 27.

[0078] According to one embodiment, shown in Figures 1, 2 and 5, one (or more) pressure regulator 630 is interposed on the oxygen ejection line 63 to send the oxygen produced by the electrolyzer 6 to the oxygen reservoir 8. The pressure regulator 630 reduces the oxygen pressure from the electrolyzer 6 to the low-pressure oxygen reservoir 8.

[0079] According to one embodiment, in figures 1 to 5, the supply device 1 includes one (or more) water pump 64 on the water supply conduit 61 to send water from the liquid water reservoir 5 to the electrolyzer 6. The water pump 64 is driven by a first motor 65.

[0080] According to one embodiment, shown in Figures 3 and 4, the first motor 65 comprises a rotating shaft 68 for driving the water pump 64. One (or more) blade (or blades) 66 is disposed in the hydrogen ejection conduit 62 and is driven in rotation about a rotation axis 67 by the hydrogen flow from the electrolyzer 6 to the hydrogen reservoir 3 in the hydrogen ejection conduit 62. The drive shaft 68 of the first motor 65 for driving the water pump 64 is coupled to the rotation axis 67 of the blade 66 to recover the energy of the blade 66 when the blade 66 is set in rotation by the hydrogen flow from the electrolyzer 6 to the hydrogen reservoir 3 in the hydrogen ejection conduit 62. This allows energy to be recovered at the output of the electrolyzer 6. This reduces the amount of energy consumed by the motor 35 driving the water pump 64.

[0081] According to one embodiment, in figures 1 to 4, the electrolyzer 6, the water inlet duct 61, the hydrogen ejection duct 62, the oxygen ejection duct 63, the liquid water tank 5, the low pressure hydrogen tank 3, the fuel cell 2, the hydrogen inlet duct 21, the oxygen inlet duct 22, the water ejection duct 23 and the water condenser 4 are part of the same unit or assembly, entirely onboard the aircraft or the airship.

[0082] According to one embodiment in [Fig. 5], the electrolyzer 6, the water inlet duct 61, and the liquid water tank 5 form part of a first unit 100 or first assembly 100. The low-pressure hydrogen tank 3, the fuel cell 2, the hydrogen inlet duct 21, the oxygen inlet duct 22, and the water condenser 4 form part of a second unit 200 or second assembly 200, which is separable from the first unit 100. The first unit 100 or first assembly 100 can, for example, be fixed to the ground. The second unit 200 or second assembly 200 can, for example, be mounted on the aircraft or on the airship. The second unit 200 can be connected to the first unit 100 to send hydrogen generated by electrolyzer 6 to hydrogen tank 3, to send oxygen generated by electrolyzer 6 to oxygen line 63, and to send liquid water supplied by The water condenser 4 connects to the liquid water reservoir 5. The hydrogen ejection line 62 may include a first hydrogen passage interface 621 in the first unit 101 and a second hydrogen passage interface 622 in the second unit 200, the second interface 622 being able to be connected to the first interface 621 and disconnected from the first interface 621. The oxygen ejection line 63 may include a first oxygen passage interface 631 in the first unit 101 and a second oxygen passage interface 632 in the second unit 200, the second interface 632 being able to be connected to the first interface 631 and disconnected from the first interface 631.The water ejection conduit 23 may include a first water passage interface 231 in the first unit 101 and a second water passage interface 232 in the second unit 200, the second interface 232 being able to be connected to the first interface 231 and disconnected from the first interface 231. The second circulation circuit 70 of the second heat transfer fluid may include a third circulation circuit of the heat transfer fluid for cooling the electrolyzer 6 located on the first unit 100 and a fourth circulation circuit of the heat transfer fluid for cooling the fuel cell 2, which is located on the second unit 200 and which is separate from the third circuit.

[0083] According to one embodiment, in figures 1 to 5, an initial mass of gaseous hydrogen is contained in the hydrogen reservoir 3.

[0084] According to one embodiment, in figures 1 to 5, the electrolyzer 6 can be formed by a reversible module that can operate either as an electrolyzer or as a fuel cell.

[0085] According to one embodiment, in figures 1 to 5, the fuel cell 2 can be formed by a reversible module that can operate either as an electrolyzer or as a fuel cell.

[0086] Thanks to the invention, the system is simplified (low-pressurized hydrogen tank 3, which can be incorporated into the envelope of an airship) and a reduction in the onboard mass is achieved (low-pressure vs. high-pressure pump and compressor system). Improved efficiency and operability are obtained.

[0087] Of course, the embodiments, features, possibilities and examples described above can be combined with each other or selected independently of each other.

Claims

Demands

1. A hydrogen supply device for an aircraft, the device comprising at least one low-pressure hydrogen tank (3), at least one water reservoir (5), at least one fuel cell (2), comprising at least one hydrogen inlet conduit (21) connected to the hydrogen reservoir (3), at least one oxygen inlet conduit (22), and at least one water discharge conduit (23) for the ejection of water produced by the combustion of hydrogen by the fuel cell (2) to generate electricity on at least one power output (24) of the fuel cell (2), the water discharge conduit (23) being connected to the water reservoir (5), at least one electrolyzer (6), comprising at least one water inlet conduit (61) connected to the water reservoir (5), and at least one hydrogen discharge conduit (62) for the ejection of hydrogen produced by the electrolysis of water in the electrolyzer (6), which is connected to the first hydrogen reservoir (3), at least one oxygen ejection conduit (63) produced by electrolysis of water in the electrolyzer (6) and at least one electricity supply inlet (69), characterized in that the device further comprises at least one switch (10) configured to switch an electrical circuit (200) of the aircraft either to the fuel cell power output (24) in a first switching position, or to the electrolyzer power input (69) in a second switching position, the switch (10) being controllable to be either in the first switching position or in the second switching position, The device includes at least one water pump (64) on the water inlet conduit (61) for sending water from the liquid water reservoir (5) to the electrolyzer (6), a first motor (65) having a rotating shaft (68) for driving the water pump (64), and at least one blade (66), which is disposed in the hydrogen ejection conduit (62) and is driven in rotation about an axis (67) by the hydrogen flow from the electrolyzer (6) to the hydrogen reservoir (3) in the hydrogen ejection conduit (62), the drive shaft (68) of the first pump-driving motor (65) (64) water being coupled to the axis (67) of rotation of the blade (66) to recover the energy of the blade (66).

2. Device according to claim 1, characterized in that the switch (10) comprises a first electrical terminal (101) connected to the power output (24) of the fuel cell (2), a second electrical terminal (102) connected to the power input (69) of the electrolyzer (6), and a third electrical terminal (103) connected to at least one electrical circuit (200) of the aircraft, in the first switching position the switch (10) connecting the third electrical terminal (103) to the first electrical terminal (101) and the third electrical terminal (103) not being connected to the second electrical terminal (102), to operate the fuel cell (2) on the electrical circuit (200) of the aircraft without operating the electrolyzer (6),and in the second switching position, the switch (10) connecting the third electrical terminal (103) to the second electrical terminal (102), and the third electrical terminal (103) not being connected to the first electrical terminal (101), to operate the electrolyzer (6) on the aircraft's electrical circuit (200) without operating the fuel cell (2), the device includes at least one electrical converter (9) connected between the third electrical terminal (103) of the switch (10) and the aircraft's electrical circuit (200), the third electrical terminal (103) of the switch (10) is connected to at least one electrically consuming device (201) of the aircraft's electrical circuit (200) in the first switching position, the third electrical terminal (103) of the switch (10) is connected to at least one electrically supplying device (202) of the aircraft's electrical circuit (200) in the second switching position.

3. Device according to claim 1 or 2, characterized in that the device (202) for supplying electricity to the electrical circuit (200) of the aircraft comprises at least one photovoltaic panel (203).

4. Device according to any one of the preceding claims, characterized in that on the water ejection conduit (23) at least one water condenser (4) is interposed to send liquid water in the water ejection conduit (23) to the liquid water reservoir (5).

5. Device according to claim 4, characterized in that it comprises a first circuit (40) for circulating a first heat transfer fluid For cooling the water condenser (4), the first circulation circuit (40) of the first heat transfer fluid passing through or against the water condenser (4) and comprising at least one first heat exchanger (41) capable of removing heat from the water condenser (4) via at least one first pipe (42, 43) carrying the first heat transfer fluid of the first circuit (40), and / or a second circulation circuit (70) of a second heat transfer fluid for cooling the fuel cell (2) and the electrolyzer (6), the second circulation circuit (70) of the second heat transfer fluid passing through or against the fuel cell (2) and through or against the electrolyzer (6) and comprising at least one second heat exchanger (71) capable of removing heat from the fuel cell (2) and the electrolyzer (6) via at least one second pipe (72, 73,74) passage of the second heat transfer fluid of the second circuit (70).

6. Device according to claim 5, characterized in that the first heat exchanger (41) and / or the second heat exchanger (71) is of the grid and / or fin type and comprises at least one air fan (45), capable of extracting heat from the first heat exchanger (41) and / or the second heat exchanger (71) via air.

7. Device according to claim 5 or 6, characterized in that the first heat exchanger (41) is separated from the second heat exchanger (71).

8. Device according to claim 5 or 6, characterized in that the first heat exchanger (41) is connected to the second heat exchanger (71).

9. Device according to any one of the preceding claims, characterized in that at least one pressure regulator (620) is interposed on the hydrogen ejection conduit (62) for sending the hydrogen produced by the electrolyzer (6) to the first hydrogen reservoir (3) with lowering of the hydrogen pressure from the electrolyzer (6) to the low pressure hydrogen reservoir (3).

10. A device according to any one of the preceding claims, characterized in that the low-pressure hydrogen reservoir (3) contains hydrogen in the gaseous state, the low-pressure hydrogen reservoir (3) contains hydrogen in the gaseous state at a pressure greater than 100 to 500 mbar relative to ambient pressure.

11. A device according to any one of the preceding claims, characterized in that the oxygen supply duct (22) is connected to an ambient air inlet (25).

12. Device according to any one of claims 1 to 10, characterized in that it further comprises at least one oxygen reservoir (8), which is connected to the oxygen ejection conduit (63) to receive oxygen produced by the electrolyzer (6).

13. A device according to any one of claims 1 to 10, characterized in that it further comprises an oxygen reservoir (8), which is connected to the oxygen ejection conduit (63) to receive oxygen produced by the electrolyzer (6), the oxygen supply conduit (22) being connected to an ambient air inlet (25) and to another oxygen supply conduit (26) from the oxygen reservoir (8) to allow oxygen to be sent from both the ambient air inlet (25) and the oxygen reservoir (8) to the oxygen supply conduit (22).

14. Device according to claim 13, characterized in that the oxygen supply conduit (22) is connected to the ambient air inlet (25) and to the other oxygen supply conduit (26) from the oxygen reservoir (8) at least via an air regulator (27).

15. Device according to any one of the preceding claims, characterized in that the electrolyzer (6), the water inlet conduit (61) and the liquid water reservoir (5) are part of a first unit (100), the low-pressure hydrogen reservoir (3), the fuel cell (2), the hydrogen inlet conduit (21), the oxygen inlet conduit (22) and the water condenser (4) are part of a second unit (200), which is separable from the first unit (100).

16. Device according to any one of the preceding claims, characterized in that an initial mass of gaseous hydrogen is contained in the hydrogen reservoir (3).

17. Device according to any one of the preceding claims, characterized in that the electrolyzer (6) can be formed by a reversible module capable of operating either as an electrolyzer or as a fuel cell.

18. Dirigible aerostat, comprising at least one feeding device (1) according to any one of the preceding claims.

19. Method of supplying hydrogen to an aircraft using the device (1) power supply according to any one of claims 1 to 17, characterized in that the switch (10) is controlled either in the first switching position or in the second switching position.

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